1.南昌航空大学 飞行器工程学院,南昌 330063
2.中国航天科技集团有限公司 西安航天动力技术研究所,西安 710025
3.华中科技大学 航空航天学院,武汉 430074
孙迪(1989-),女,讲师,硕士,研究方向为固体火箭发动机总体设计。E⁃mail:sundi2021@126.com
李永洲(1984-),男,副教授,博士,研究方向为组合发动机总体设计。E⁃mail:nuaa⁃2004@126.com
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孙迪, 李永洲, 刘晓伟, 等. 横向变过载对固体火箭发动机绝热结构设计的影响[J]. 航空动力学报, 2021,36(11):2458-2464.
Di SUN, Yongzhou LI, Xiaowei LIU, et al. Influence of transverse variable acceleration on design of insulation structure for solid rocket motor[J]. Journal of Aerospace Power, 2021, 36(11): 2458-2464.
孙迪, 李永洲, 刘晓伟, 等. 横向变过载对固体火箭发动机绝热结构设计的影响[J]. 航空动力学报, 2021,36(11):2458-2464. DOI: 10.13224/j.cnki.jasp.20200435.
Di SUN, Yongzhou LI, Xiaowei LIU, et al. Influence of transverse variable acceleration on design of insulation structure for solid rocket motor[J]. Journal of Aerospace Power, 2021, 36(11): 2458-2464. DOI: 10.13224/j.cnki.jasp.20200435.
针对新一代防空导弹高机动作战特点,研究了复杂横向变过载对固体火箭发动机绝热结构工程设计的影响。同时考虑过载值和过载角度的瞬时变化,对发动机绝热层进行网格划分,并对烧蚀厚度进行编程计算,进而按照安全裕度设计准则得到不同位置的绝热层设计厚度。与传统设计结果相比,考虑横向过载的变化可以显著减少了发动机的结构质量,提高了发动机总体性能,绝热质量减小了53.7%,总冲提高了6.84%。
Targeting the high⁃mobility characteristics of the new generation antiaircraft missiles,the influence of the complex transverse variable acceleration trajectory on the engineering design for the solid rocket motor insulation structure was studied.It considered the instantaneous changes of acceleration value and angle,meshed the insulation structure,and calculated its ablation thickness by programming,and then the design thickness of the heat insulation layer at different positions was obtained according to the safety margin design criterion.Compared with traditional design results,considering the change of transverse acceleration significantly reduced the structural mass of the motor,and improved the overall performance;the heat insulation mass of the motor was reduced by 53.7%,and the total impulse was increased by 6.84%.
袁华 , 简金蕾 , 任宏滨 , 等 . 第4代防空导弹关键技术初探 [J]. 现代防御技术 , 2007 , 35 ( 5 ): 51 ⁃ 54 .
YUAN Hua , JIAN Jinlei , REN Hongbin , et al . Initially research on the key technologies of the fourth generation of antiaircraft missile [J]. Modern Defence Technology , 2007 , 35 ( 5 ): 51 ⁃ 54 . (in Chinese)
陈海建 . 先进防空导弹关键技术分析及发展启示 [J]. 现代防御技术 , 2020 , 48 ( 4 ): 60 ⁃ 66 .
CHEN Haijian . Key technology analysis and development enlightenment of advanced air defense missile [J]. Modern Defence Technology , 2020 , 48 ( 4 ): 60 ⁃ 66 . (in Chinese)
李江 , 何国强 , 秦飞 , 等 . 高过载条件下绝热层烧蚀实验方法研究(Ⅰ)方案论证及数值模拟 [J]. 推进技术 , 2003 , 24 ( 6 ): 315 ⁃ 318 .
LI Jiang , HE Guoqiang , QIN Fei , et al . Study of experimental method for ablation of insulator of SRM with high acceleration(Ⅰ) [J]. Journal of Propulsion Technology , 2003 , 24 ( 6 ): 315 ⁃ 318 . (in Chinese)
张翔宇 , 高波 , 甘晓松 , 等 . 飞行过载对固体火箭发动机不稳定燃烧的影响 [J]. 宇航学报 , 2019 , 40 ( 8 ): 972 ⁃ 976 .
ZHANG Xiangyu , GAO Bo , GAN Xiaosong , et al . Impacts of flight acceleration on combustion instability of solid rocket motor [J]. Journal of Astronautics , 2019 , 40 ( 8 ): 972 ⁃ 976 . (in Chinese)
孙迪 , 马亮 , 甘晓松 , 等 . 嵌金属丝两级药柱掺混燃烧下的内弹道计算 [J]. 火箭推进 , 2019 , 45 ( 3 ): 59 ⁃ 63 .
SUN Di , MA Liang , GAN Xiaosong , et al . Internal ballistics calculation under mixing combustion of two⁃stage grain with embedded wire [J]. Journal of Rocket Propulsion , 2019 , 45 ( 3 ): 59 ⁃ 63 . (in Chinese)
MITANI T , NIILKA T . An analytical and experimental study for solid⁃propellant combustion in an acceleration [J]. Combustion Science and Technology , 1973 , 8 ( 3 ): 61 ⁃ 66 .
BORAAS S . Modeling slag deposition in the space shuttle solid rocket motor [J]. Journal of Spacecraft and Rockets , 1984 , 21 ( 1 ): 47 ⁃ 54 .
刘世东 . 过载对固体火箭发动机影响的研究 [J]. 航空兵器 , 2006 , 6 : 42 ⁃ 44 .
LIU Shidong . Influence of acceleration load on solid rocket motor [J]. Aero Weaponry , 2006 , 6 : 42 ⁃ 44 . (in Chinese)
田维平 , 许团委 , 王建儒 . 过载下燃烧室粒子特性与绝热层烧蚀研究进展 [J]. 固体火箭技术 , 2015 , 38 ( 1 ): 30 ⁃ 37 .
TIAN Weiping , XU Tuanwei , WANG Jianru . Progress on condensed⁃phase particle characteristic and insulation ablation in SRM chamber with flight overload [J]. Journal of Solid Rocket Technology , 2015 , 38 ( 1 ): 30 ⁃ 37 . (in Chinese)
KOVALEV O B . Motor and plume particle size prediction in solid⁃propellant rocket motors [J]. Journal of Propulsion and Power , 2002 , 18 ( 6 ): 1199 ⁃ 1210 .
BAKER K , CROWE C T , WILLOUGHBY P . A photographic and analytic study of composite propellant combustion in an acceleration field [J]. Journal of Spacecraft and Rockets , 1971 , 8 ( 4 ): 310 ⁃ 317 .
KING M K . Critical review: modeling of acceleration effects on solid propellant combustion [J]. AIAA Journal , 1976 , 14 ( 1 ): 18 ⁃ 25 .
LANGHENRY M T . Acceleration effects in solid propellant rocket motors [R].AIAA 1986 ⁃1577 , 1986 .
SABNIS J S , DE JONG F J , GIBELING H J . Calculation of particle trajectories in solid rocket motors with arbitrary acceleration [J]. Journal of Propulsion and Power , 1992 , 8 ( 5 ): 961 ⁃ 967 .
DERBIDGE C , POWARS C . Acceleration effects on internal insulation erosion [R].AIAA 1993⁃ 1858 ,1993.
何国强 , 王国辉 , 蔡体敏 , 等 . 高过载条件下固体发动机内流场及绝热层冲蚀研究 [J]. 固体火箭技术 , 2001 , 24 ( 4 ): 4 ⁃ 8 .
HE Guoqiang , WANG Guohui , CAI Timin , et al . Investigation on internal flow and insulator erosion of SRM under high acceleration [J]. Journal of Solid Rocket technology , 2001 , 24 ( 4 ): 4 ⁃ 8 . (in Chinese)
刘洋 , 李江 , 杨飒 , 等 . 过载条件下EPDM绝热材料烧蚀机理和模型研究:Ⅰ 烧蚀机理分析 [J]. 固体火箭技术 , 2011 , 34 ( 2 ): 229 ⁃ 233 .
LIU Yang , LI Jiang , YANG Sa , et al . Investigation on ablation mechanism and model of EPDM insulator under high acceleration condition:Ⅰ analysis of ablation mechanism [J]. Journal of Solid Rocket Technology , 2011 , 34 ( 2 ): 229 ⁃ 233 . (in Chinese)
李江 , 何国强 , 陈剑 , 等 . 高过载条件下绝热层烧蚀实验方法研究:Ⅱ 收缩管聚集法 [J]. 推进技术 , 2004 , 25 ( 3 ): 196 ‑ 198 .
LI Jiang , HE Guoqiang , CHEN Jian , et al . Study of experimental method for ablation of insulator of SRM with high acceleration:Ⅱ convergent tube experimental method [J]. Journal of Propulsion Technology , 2004 , 25 ( 3 ): 196 ⁃ 198 . (in Chinese)
李越森 , 叶定友 , 利凤祥 . 横向加速度对飞行发动机绝热层烧蚀影响的试验研究 [J]. 航空动力学报 , 2004 , 19 ( 2 ): 278 ‑ 282 .
LI Yuesen , YE Dingyou , Li Fengxiang . An experimental study of SRM insulation erosion performance under transverse g⁃load in flight [J]. Journal of Aerospace Power , 2004 , 19 ( 2 ): 278 ⁃ 282 . (in Chinese)
诸毓武 . 某导弹主动段全程横向过载条件下发动机绝热层安全性分析 [J]. 上海航天 , 2013 , 30 ( 2 ): 56 ⁃ 59 .
ZHU Yuwu . Security analysis of motor insulation under whole process transverse overload for some missile in boost phase [J]. Aerospace Shanghai , 2013 , 30 ( 2 ): 56 ⁃ 59 . (in Chinese)
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